WO2023149386A1

WO2023149386A1 - Satellite control method

Info

Publication number: WO2023149386A1
Application number: PCT/JP2023/002763
Authority: WO
Inventors: 敦田中
Original assignee: ＳｋｙＤｅｅｒ株式会社
Priority date: 2022-02-01
Filing date: 2023-01-29
Publication date: 2023-08-10

Abstract

Provided is a satellite control method capable of suppressing cost for purchasing, remanufacturing, operating, and the like, of an artificial satellite. A satellite control method according to the present invention comprises: a separation step for separating, from a platform satellite P that revolves while being joined together with a first mission satellite M1 along a first orbit and that supplies the first mission satellite with electric power for enabling the first mission satellite to execute a mission on a stationery orbit, the first mission satellite M1; a joining step for joining a second mission satellite M2 injected into the first orbit with the platform satellite P; and a post-joining step for causing the platform satellite P joined with the second mission satellite M2 to revolve along the first orbit or to move along another orbit different from the first orbit.

Description

Satellite control method

The present invention relates to a satellite control method.

Conventionally, a satellite has a platform unit that has basic functions such as a power supply system (power generation function, power control function), an attitude orbit control system (propulsion function, attitude orbit control function), and a thermal control function, and a mission unit that performs a predetermined mission. It is manufactured with integrated functions and operated in outer space. It is known that an artificial satellite that has reached its expiration date is discarded as a whole. Further, in the case of an artificial satellite orbiting a geostationary orbit, it is known to transfer the artificial satellite to an orbit called a graveyard orbit and discard it (see, for example, Patent Document 1). Further, it is known that when a satellite fails to perform a predetermined mission due to a failure in either the power supply system or the attitude orbit control system on orbit, the satellite is scrapped as a whole.

U.S. Patent No. 10513352

In the conventional technology, when the satellite reaches its expiration date, the entire satellite is scrapped, even though the satellite's control unit, propulsion device, power supply, etc., can still be used. However, there was a problem that the purchase cost and operation cost were high.

Alternatively, if a failure occurs in either the power supply system or the attitude orbit control system on orbit and a predetermined mission cannot be performed, the entire satellite will be scrapped even though the mission functions are still available. Therefore, there was a problem that the cost of remanufacturing the artificial satellite was high.

Therefore, the present invention has been made in view of these points, and provides a satellite control method that can reduce the cost of purchasing, remanufacturing, operating, etc. of an artificial satellite by reusing or making effective use of usable parts. intended to

A satellite control method of the present invention for solving the above problems is a satellite control method for orbiting in a first orbit in combination with a first mission satellite, and providing power for the first mission satellite to perform a mission in the first orbit. a separation step of separating the first mission satellite from a platform satellite that supplies to the first mission satellite; a coupling step of coupling the second mission satellite injected into the first orbit and the platform satellite; and a post-coupling step of causing said platform satellite coupled with said second mission satellite to orbit in said first orbit or move to another orbit different from said first orbit.

The separating step may include separating the first mission satellite from the platform satellite and injecting the first mission satellite into an orbit for entry into the atmosphere.

In the separating step, the platform satellite may be moved to another orbit different from the first orbit to separate the first mission satellite.

The method of the present invention, in a state in which the platform satellite is coupled with the first mission satellite, the second mission satellite, or the third mission satellite different from the second mission satellite, the platform satellite, It may further comprise the step of moving to a trajectory different from the first trajectory.

The platform satellite has a power generator, and the first mission satellite and the second mission satellite do not have a power generator, are detachably coupled to the platform satellite, and are powered by the platform satellite. may

The first mission satellite and/or the second mission satellite has a power supply system and/or an attitude orbit control system and is detachably coupled to the platform satellite, and the first mission satellite and/or the second mission satellite If there is a failure in the power supply system of the satellite, power may be supplied from the platform satellite.

The first mission satellite and/or the second mission satellite has a power supply system and/or an attitude orbit control system, and the power supply system and/or the attitude orbit control system fails on the first orbit. A mission satellite and/or said second mission satellite and said platform satellite may be coupled.

The platform satellite may be discarded while the first mission satellite is coupled to the platform satellite.

Further, the satellite control method of the present invention is such that the first mission satellite orbits in the geostationary orbit, which is the first orbit, and the power for the first mission satellite to execute a mission in the geostationary orbit is supplied to the first orbit. an orbital descent step of moving a platform satellite to supply one mission satellite to a second orbit closer to the earth than the first orbit; and a separation step of separating the first mission satellite from the platform satellite in the second orbit. a coupling step of coupling the second mission satellite injected into the second orbit and the platform satellite; and moving the platform satellite coupled with the second mission satellite to the first orbit, or and a trajectory moving step of moving to a third trajectory different from the second trajectory.

Further, the satellite control method of the present invention orbits in conjunction with a first mission satellite on a first orbit, and supplies power to the first mission satellite for the first mission satellite to perform a mission in the first orbit. an orbital descent step of moving a platform satellite supplied to a second orbit closer to the earth than the first orbit; a separation step of separating the first mission satellite from the platform satellite in the second orbit; a coupling step of coupling the second mission satellite injected into the second orbit and the platform satellite; and a trajectory moving step of moving to a third trajectory different from the second trajectory.

According to the present invention, there is an effect that it is possible to provide a satellite control method capable of reducing the cost of purchasing/remanufacturing/operating artificial satellites.

1 is a block diagram showing the configuration of a satellite utilization system; FIG. It is a figure which shows the structure of an artificial satellite. It is a figure which shows the state which the artificial satellite is going around the geostationary orbit. FIG. 4 is a diagram showing the movement of satellites according to the satellite control method of the embodiment of the present invention; It is a block diagram which shows the structure of a satellite management apparatus. 1 is a flow diagram of a satellite control method; FIG. FIG. 4 is a diagram showing motion of another satellite according to the satellite control method of the embodiment of the present invention; FIG. 4 is a diagram showing motion of another satellite according to the satellite control method of the embodiment of the present invention;

Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the embodiments and drawings, the same or corresponding elements are denoted by the same or corresponding reference numerals, and overlapping descriptions are appropriately omitted or simplified. FIG. 1 is a block diagram showing the configuration of the satellite utilization system S100. FIG. 2 is a diagram showing the configuration of the artificial satellite 1. As shown in FIG. FIG. 3 is a diagram showing a state in which the artificial satellite 1 is orbiting the geostationary orbit 101. As shown in FIG.

The satellite utilization system S100 of this embodiment includes an artificial satellite 1 and a satellite management device 2 on the ground. The artificial satellite 1 has a platform satellite P and a mission satellite M. Mission satellite M is a satellite detachably coupled to platform satellite P.

In the following description, the satellite 1 moves between the geostationary orbit 101 (see FIG. 3), which is the first orbit, and the geostationary transfer orbit 102, which is the second orbit. A geostationary orbit (GEO) 101 is a circular orbit whose altitude from the surface of the earth 10 is approximately 36,000 km above the equator. A geostationary transfer orbit 102 (GTO) is an orbit into which the artificial satellite 1 is temporarily injected before the artificial satellite 1 launched from the earth 10 moves to the geostationary orbit 101 . The geostationary transfer orbit 102 is an elliptical orbit whose perigee is at a lower altitude than the geostationary orbit 101 .

[Overview of satellite control method of this embodiment]
Before describing the details of the satellite utilization system S100, an outline of the satellite control method of this embodiment will be described with reference to FIG. FIG. 4 is a diagram illustrating satellite motion according to the satellite control method of the embodiment of the present invention. In the following, for example, the first mission satellite M1, which has reached the expiration date, is separated from the platform satellite P, and the second mission satellite M2 launched from the earth is newly coupled to the platform satellite P. A satellite control method will be described.

In the satellite control method of this embodiment, first, the artificial satellite 1 orbiting the geostationary orbit 101 is moved to the geostationary transfer orbit 102, which is a second orbit closer to the earth than the geostationary orbit 101 ((1 in FIG. 4). ) and (2)).

Next, the first mission satellite M1 is separated from the platform satellite P of artificial satellite 1. As a result, the platform satellite P is not coupled to the mission satellite M ((3) in FIG. 4). A second mission satellite M2 scheduled to be coupled to the platform satellite P is launched from the ground and injected into the geostationary transfer orbit 102 ((4) in FIG. 4).

Next, the platform satellite P moves toward the second mission satellite M2 on the geostationary transfer orbit 102 and couples with the second mission satellite M2 ((5) in FIG. 4).

After that, the platform satellite P coupled with the second mission satellite M2 rises again toward the geostationary orbit 101 and continues orbiting on the geostationary orbit 101 ((6) in FIG. 4).

According to the satellite control method described above, the mission satellite M coupled to the platform satellite P can be changed from the first mission satellite M1 to the second mission satellite M2. Instead of disposing of the entire satellite 1 when the deadline expires, only the first mission satellite M1 can be discarded, and the platform satellite P can continue to be used with the second mission satellite M2 coupled. can.

[Detailed Configuration of Satellite Utilization System S100]
The artificial satellite 1 has a platform satellite P and a mission satellite M as described above. Platform satellite P is the satellite to which mission satellite M is coupled. The mission satellite M is a satellite that performs a predetermined mission in outer space.

(platform satellite P)
The platform satellite P has, as shown in FIG. The platform satellite P also has, for example, structural and integration parts (not shown). The structural part here means a panel or the like necessary for the platform satellite P to maintain its shape. Also, the integration part means a cable, a bracket, and the like. Further, the solar array paddle 31 and the power source unit 32 are collectively called a power supply system, and the propulsion device 34 and the attitude control device 35 are collectively called an attitude orbit control system.

The solar paddle 31 is a power generator that converts sunlight into electric power. The solar array paddle 31 has, for example, a foldable power generation panel that is deployed in outer space.

The power supply unit 32 has a battery and a power control device (not shown), and the battery stores the power generated by the solar paddle 31 . The power supply unit 32 supplies power to each unit of the platform satellite P. FIG. The power supply unit 32 also supplies power to the mission satellite M coupled to the platform satellite P, as an example. Power supply 32 also provides power to mission satellite M, for example, so that mission satellite M can continue its mission while platform satellite P is orbiting. With such a power supply unit 32 provided, the platform satellite P supplies power to the mission satellites (first mission satellite, second mission satellite, and so on) so that the mission satellites can execute missions in predetermined orbits. (including the Nth mission satellite coupled to ).

The coupling mechanism 33 is a mechanism for coupling the platform satellite P and the mission satellite M. The coupling mechanism 33 specifically has a mechanism for mechanically coupling with the coupling mechanism 41 of the mission satellite M. As shown in FIG. The coupling mechanism 33 operates, for example, based on a control signal from the control unit 37 to switch the coupling state between the platform satellite P and the mission satellite M. FIG. When the mission satellite M is separated from the platform satellite P, the coupling mechanism 33 releases the connection between the platform satellite P and the mission satellite M, thereby separating the mission satellite M from the platform satellite P.

The propulsion device 34 is a device that generates a propulsive force for moving the platform satellite P, such as a chemical propulsion device or an electric propulsion device. Chemical propulsion devices are, by way of example, monopropellant or bipropellant thrusters. The electric propulsion device is, by way of example, an ion engine or a Hall thruster engine.

The attitude control device 35 is a device for controlling the attitude of the platform satellite P, and has attitude sensors and actuators (not shown). Attitude sensors are devices such as gyroscopes, earth sensors, sun sensors, star trackers and magnetic sensors. Actuators are devices such as momentum wheels, reaction wheels and control moment gyros.

The attitude control device 35 has, for example, a device (not shown) that measures the relative distance between the platform satellite P and the mission satellite M flying away from the platform satellite P in outer space. The attitude control device 35 also has a device for measuring the attitude of the mission satellite M, a device for specifying the state of motion of the mission satellite M, and the like.

The communication device 36 is, for example, a device that communicates with the communication device 44 of the mission satellite M and the satellite management device 2 on the ground. The communication device 36 transmits various data related to the platform satellite P, for example, to the satellite management device 2 . The communication device 36 may also transmit various data regarding the mission satellites M coupled to the platform satellite P to the satellite manager 2 . The communication device 36 receives various command signals transmitted by the satellite management device 2 .

For example, the communication device 36 may transmit the following information to the satellite management device 2 in order to notify the satellite management device 2 that the mission satellite M needs to be replaced. Specifically, the communication device 36 provides information indicating that the first mission satellite M1 coupled to the platform satellite P has failed, and information indicating that the first mission satellite M1 has expired and operation has ended. , or information indicating that the first mission satellite M1 needs to be replaced. Such information may be directly transmitted by the first mission satellite M1 itself to the satellite management device 2 and/or a mission control device (not shown) on the ground different from the satellite management device 2 .

The control unit 37 is a computer that controls the operation of each unit of the platform satellite P. For example, the control unit 37 controls the operation of the coupling mechanism 33 to couple or separate the platform satellite P and the mission satellite M. The control unit 37 also controls the coupling mechanism 33 and the propulsion device 34 to separate the mission satellite M from the platform satellite P such that, as an example, the mission satellite M moves to a fourth orbit that enters the atmosphere. The controller 37 also controls the operation of the propulsion device 34 to move the platform satellite P. In this embodiment, platform satellite P moves from geostationary transfer orbit 102 to geostationary orbit 101 and from geostationary transfer orbit 102 to geostationary orbit 101 .

The fourth orbit is the orbit for re-entering the atmosphere of the mission satellite M separated from the platform satellite. There may be. For example, a trajectory in which the separated mission satellite M enters the atmosphere over five years may be used. It does not matter how long it takes for the mission satellite M to enter the atmosphere after it is separated from the platform satellite P. A mode may be adopted in which a fall area is determined and the mission satellite is controlled to plunge into the atmosphere. It should be noted that the mission satellite M separated from the platform satellite P may be put into any orbit. It may be a trajectory.

The thermal control unit 38 is a control unit that controls the temperature of devices such as heaters and temperature sensors provided on the platform satellite P, and is controlled by the control unit 37, for example.

(Mission satellite M)
The mission satellite M has, as shown in FIG. The mission satellite M is, for example, a satellite that performs a mission related to meteorological observation, a mission related to land observation or ocean observation, a mission related to positioning such as a global positioning system (GPS), a mission related to air traffic management, or a mission related to communication. is. The mission satellite M, like the platform satellite P, also has, for example, a structural part and an integration part (not shown). In this application, a "mission" is not a temporary mission, such as transferring certain equipment, cargo, or satellites, etc. from a geostationary transfer orbit to a geostationary orbit, but a long-term orbital mission, such as a meteorological observation mission, as described above. It refers to ongoing missions.

The connection mechanism 41 is a mechanism for connecting the platform satellite P and the mission satellite M. The coupling mechanism 41 has a mechanism for mechanically coupling with the coupling mechanism 33 of the platform satellite P, for example.

The mission device 42 is a device for executing the mission that the mission satellite M should perform in outer space, and has various measuring instruments, for example. The power distribution device 43 is a device that supplies power supplied from the platform satellite P to each device provided on the mission satellite M. FIG.

The communication device 44 is a device that communicates with each of the communication device 36 of the platform satellite P and the mission control device on the ground. The communication device 44, for example, transmits various data obtained by the mission satellite M executing a mission to the platform satellite P and/or the mission control device on the ground.

The control unit 45 is a computer that controls the operation of each part of the mission satellite M. Specifically, the control unit 45 controls operations of the coupling mechanism 41, the mission device 42, the power distribution device 43, the communication device 44, the heat control unit 46, and the like. The thermal control unit 46 is a control unit that controls the temperature of equipment such as a heater and a temperature sensor provided on the mission satellite M, and is controlled by the control unit 45, for example.

In this embodiment, communication between the communication device 44 and the communication device 36 is exemplified, but the present invention is not necessarily limited to this. Mission satellite M may not have the capability to communicate with platform satellite P. In this embodiment, the control unit 45 controls the operation of the connection mechanism 41, but if the connection mechanism 41 does not have an operable structure, the control unit 45 controls the connection mechanism 41. do not need to be controlled. Specifically, for example, if the coupling mechanism 41 is configured by a structure (for example, a handle) to which the coupling mechanism 33 of the platform satellite P is coupled, control by the control unit 45 is unnecessary.

Unlike the platform satellite P in this embodiment, the mission satellite M does not include the solar array paddle 31, the power supply unit 32, the propulsion device 34, and the attitude control device 35. When the mission satellite M is configured in this way, there is an advantage that the mission satellite M can be made small and light. Furthermore, since the mission satellite M does not need to perform most of the various post-production/pre-launch tests that have been performed with the conventional technology, it is possible to reduce costs and greatly shorten the development period.

It is not essential in the present invention that the mission satellite M does not have the solar array paddle 31, the power supply unit 32, the propulsion device 34, the attitude control device 35, etc., and the mission satellite M may have these devices. .

Also, the mission satellite M equipped with a power supply system (solar battery paddle 31, power supply unit 32) and an attitude orbit control system (propulsion device 34, attitude control device 35) is operated in orbit by the power supply system and/or the attitude orbit control system. may have failed.

In the satellite utilization system S100 of this embodiment, for example, after the first mission satellite M1 is used, the platform satellite P is coupled with the second mission satellite M2 launched from the earth. The fact that the mission satellite M can be made small and light as described above is advantageous in that the second mission satellite M2, which is coupled to the platform satellite P, can be launched with a smaller rocket.

When launching the platform satellite P and the mission satellite M, the platform satellite P and the mission satellite M may be launched by the same rocket (not shown) or may be launched by separate rockets.

(Satellite management device 2)
FIG. 5 is a block diagram showing the configuration of the satellite management device 2. As shown in FIG. The satellite management device 2 is a device placed on the ground and has a communication section 21 , a storage section 22 and a control section 23 .

The communication unit 21 communicates with the artificial satellite 1. Specifically, the communication unit 21 receives signals transmitted from the platform satellite P of the artificial satellite 1 and transmits various command signals to the platform satellite P. FIG.

The storage unit 22 is a storage medium that stores various data, and includes a ROM (Read Only Memory), a RAM (Random Access Memory), a hard disk, and the like. The storage unit 22 stores computer programs executed by the control unit 23 .

The control unit 23 has a CPU (Central Processing Unit) and the like. The control unit 23 functions as a data acquisition unit 24 , a condition determination unit 25 , a signal generation unit 26 and a transmission unit 27 by executing computer programs stored in the storage unit 22 .

The data acquisition unit 24 receives signals transmitted from the platform satellite P via the communication unit 21 and acquires various data.

The condition determination unit 25 is a functional unit that determines various conditions regarding the operation of the platform satellite P and the mission satellite M. The condition determining unit 25 autonomously determines operating conditions for the platform satellite P and the mission satellite M based on various parameters relating to the operation of the platform satellite P and the mission satellite M, for example. The condition determining unit 25 may also determine operating conditions for the platform satellite P and the mission satellite M by accepting conditions determined by the operator.

Here, the condition determining unit 25 determines various conditions regarding the operation of the mission satellite M, but the condition determining unit 25 may determine only various conditions regarding the operation of the platform satellite P. good. That is, in the present invention, whether or not the satellite management device 2 controls the mission satellite M is optional.

(Processing to determine the time zone)
When the platform satellite P is moved from the geostationary orbit 101 to the geostationary transfer orbit 102 in order to couple the second mission satellite M2 to the platform satellite P (FIG. 4), at what time period does the platform satellite P move from the geostationary orbit 101 to the geostationary transfer orbit? A decision needs to be made to start moving towards 102 .

Therefore, the condition determination unit 25 determines the time slot for starting the movement of the platform satellite P. Specifically, the condition determining unit 25 first determines whether the platform satellite P is stationary based on the first time zone in which the second mission satellite M2 scheduled to be coupled to the platform satellite P should reach the geostationary orbit 101. A second time period to reach the transfer trajectory 102 is determined. Then, the condition determination unit 25 determines a third time period for starting the movement of the platform satellite P toward the geostationary transfer orbit 102 based on the second time period.

As a specific example, it is assumed that the second mission satellite M2 needs to reach the geostationary orbit 101 by "April 1, 2022", which is the first time zone. The condition determination unit 25 determines the time period before the first time period as the time period in which the platform satellite P should reach the geostationary transfer orbit 102 (second time period). Then, the condition determining unit 25 sets the time period before the second time period so that the platform satellite P reaches the geostationary transfer orbit 102 in the second time period. A time period (third time period) for starting movement toward the transfer orbit 102 is determined.

By moving the platform satellite P according to the time period thus determined by the condition determination unit 25, the platform satellite P and the second mission satellite M2 can be systematically coupled.

(Processing to determine position)
The condition determination unit 25 also determines a target position to be reached by the platform satellite P when the platform satellite P is lowered to the geostationary transfer orbit 102 . The condition determining unit 25 determines the target position of the platform satellite P based on, for example, the position in the geostationary transfer orbit 102 that the second mission satellite M2 should reach. Specifically, the condition determination unit 25 determines a position that is a distance X [m] away from the second mission satellite M2 as the target position.

The signal generation unit 26 generates a command signal including information on various operating conditions determined by the condition determination unit 25 . The signal generator 26 generates various signals related to the operations of the platform satellite P and the mission satellite M. Specifically, for example, a command signal (third command signal). This command signal may contain only information that serves as a trigger for causing the platform satellite P to start a predetermined operation, or information indicating the operating conditions of predetermined equipment (for example, the coupling mechanism 33, etc.) of the platform satellite P. may contain

The signal generation unit 26 may also generate a command signal (fourth command signal) for moving the platform satellite P from the geostationary transfer orbit 102 to the geostationary orbit 101 . This command signal may also contain only information serving as a trigger for causing the platform satellite P to start a predetermined operation, or information indicating the operating conditions of predetermined equipment (for example, the propulsion device 34, etc.) of the platform satellite P. may contain

The transmission unit 27 transmits the command signal generated by the signal generation unit 26 to the platform satellite P via the communication unit 21 . The transmitting unit 27 may transmit, for example, a command signal for starting the movement of the platform satellite P to the geostationary transfer orbit 102 to the platform satellite P as the first command signal. The first command signal may include information of the target position determined based on the position in the geostationary transfer orbit 102 that the second mission satellite M2 should reach, determined by the condition determination unit 25 .

The transmission unit 27 may also transmit a command signal for separating the first mission satellite M1 from the platform satellite P to the platform satellite P as a second command signal. The second command signal may contain information of the operating conditions under which platform satellite P separates first mission satellite M1.

The transmission unit 27 also transmits the third command signal and the fourth command signal generated by the signal generation unit 26 to the platform satellite P. Note that each of the first to fourth command signals may include a plurality of commands.

(Example of satellite control method)
An example of a satellite control method in the satellite utilization system S100 configured as described above will be described with reference to FIGS. 4 and 6. FIG. FIG. 6 is a flow diagram of a satellite control method. In the initial state of FIG. 4 ((1) of FIG. 4), the platform satellite P to which the first mission satellite M1 is coupled is orbiting the geostationary orbit 101 . Instead of moving the platform satellite P from the geostationary orbit 101 to the geostationary transfer orbit 102 and coupling with a new mission satellite, the platform satellite P may remain positioned in a predetermined orbit and may be coupled with a mission satellite launched from the earth. . Such a control method is illustrated in FIG.

First, in step S1, which is an orbital descent step, the platform satellite P is lowered from the geostationary orbit 101 to the geostationary transfer orbit 102 . Specifically, the platform satellite P receives the first command signal for starting the descent of the platform satellite P transmitted by the satellite management device 2 . The platform satellite P starts moving from the geostationary orbit 101 to the geostationary transfer orbit 102 when it receives this first command signal.

Note that "to start moving when a command signal is received" does not necessarily mean that the platform satellite P starts moving immediately upon receiving the command signal. , the platform satellite P begins to move.

After reaching the geostationary transfer orbit 102, the platform satellite P moves to a target position determined based on the position on the geostationary transfer orbit 102 to be reached by the second mission satellite M2, which is included in the first command signal as an example. .

The second mission satellite M2 is launched by a rocket from the ground, is put into the geostationary transfer orbit 102, and is positioned at a predetermined position in the geostationary transfer orbit 102 during a predetermined time period.

Then, in a separation step, step S2, the platform satellite P separates the first mission satellite M1. For example, based on the second command signal for separating the first mission satellite transmitted from the satellite management device 2, the platform satellite P separates the first mission satellite M1 according to the separation operation conditions indicated by this signal. As an example, platform satellite P launches first mission satellite M1 into fourth orbit. As a result, the first mission satellite M1 is burned in the atmosphere and discarded.

Next, in step S3, which is a combining step, the platform satellite P from which the first mission satellite M1 has been separated into a single unit moves toward the second mission satellite M2 located at a predetermined position on the geostationary transfer orbit 102. do. Platform satellite P then mates with second mission satellite M2. Platform satellite P is coupled to second mission satellite M2, for example, by mechanically coupling coupling 33 of platform satellite P and coupling 41 of second mission satellite M2.

Power is supplied from the platform satellite P to the second mission satellite M2 coupled to the platform satellite P, thereby enabling the second mission satellite M2 to perform a predetermined mission.

Next, in step S4, which is an orbit raising step (orbit moving step), the platform satellite P coupled with the second mission satellite M2 is raised to the geostationary orbit 101 again. Specifically, the platform satellite P moves to a predetermined position on the geostationary orbit 101 indicated by the positional information based on the positional information indicating the position in the geostationary orbit 101 where the second mission satellite M2 should be located. After that, the platform satellite P orbits the geostationary orbit 101 with the second mission satellite M2 coupled thereto, and the second mission satellite M2 performs a predetermined mission in the geostationary orbit 101.

(Action and effect of the present embodiment)
According to the satellite control method of the present embodiment described above, for example, when the first mission satellite M1 reaches its expiration date, instead of discarding the entire artificial satellite 1, only the first mission satellite M1 is discarded and the platform Satellite P can continue to be used with second mission satellite M2 coupled. In other words, since the platform satellite P can be used for a long period of time by replacing the mission satellite M, the cost of purchasing/operating the artificial satellite 1 can be reduced as a result. Also, since the entire satellite 1 is not discarded, the amount of waste is also reduced.

In the satellite control method of this embodiment, the platform satellite P descended from the geostationary orbit 101 to the geostationary transfer orbit 102 for coupling with the second mission satellite M2 moves the first mission satellite M1 to the fourth After being injected into orbit, it couples to the next second mission satellite M2 without changing its orbit. Such a method is advantageous in comparison with, for example, platform satellite P moving from geostationary orbit 101 to graveyard orbit and then descending to geostationary transfer orbit 102 for disposal of first mission satellite M1. It requires less fuel for the movement of satellite P and is efficient. In addition, space disposal (to graveyard orbit) can be eliminated.

In addition, in this embodiment, the mission satellite M does not have a power generator or the like, and is detachably coupled to the platform satellite P so that power is supplied from the platform satellite P. Therefore, the mission satellite M can be made small, light, and easy.

(Modification of the first embodiment)
This embodiment is not limited to the specific aspects described above, and may be modified as follows, for example. For example, although the geostationary orbit 101 and the geostationary transfer orbit 102 are illustrated above as the first orbit and the second orbit, the first orbit and the second orbit may be other arbitrary orbits. The first trajectory and the second trajectory may be the same trajectory.

Also, the platform satellite P may move the second mission satellite M2 not to the geostationary orbit 101 but to a third orbit different from the first orbit and the second orbit. Here, the third orbit may be, for example, a middle orbit or a quasi-zenith orbit. In the above embodiment, the satellite launched from the ground is exemplified to move to the first orbit after being injected into the second orbit, but the satellite may be injected directly into the first orbit. Also, in one form of the invention, the first mission satellite M1 may be separated in the first orbit and then coupled with the second mission satellite M2 without the platform satellite P moving to the second orbit ( See Figure 7). Here, the second mission satellite M2 may be directly injected into the first orbit, or may be injected into the first orbit via the second orbit. Further, as a post-coupling step, the platform satellite P coupled with the second mission satellite M2 may continue to orbit the first orbit, or may be moved to another orbit different from the first orbit. Other trajectories may be, for example, the third trajectory.

In the above description, the first mission satellite M1 is rammed into the atmosphere, but the platform satellite P does not ram the first mission satellite M1 into the atmosphere. Satellite M1 may be separated. Platform satellite P may separate first mission satellite M1, for example, in a graveyard orbit. The graveyard orbit is, for example, an orbit higher than the geostationary orbit by about 200 km to 300 km.

Although the single platform satellite P orbiting the geostationary orbit 101 and the geostationary transfer orbit 102 is illustrated above, multiple platform satellites P launched by rockets may orbit the geostationary orbit 101.

In this case, each satellite is controlled such that, for example, the satellite management device 2 selects one platform satellite P from among a plurality of platform satellites P and couples the selected platform satellite P with the second mission satellite M2. may

<Modification>
(Method of introducing platform satellite P and mission satellite M into orbit)
In the above embodiments, it was explained that the platform satellite P and the mission satellite M were launched by the same or separate rockets. In the present invention, the introduction of the platform satellite P and the mission satellite M into the geostationary orbit 101 or the geostationary transfer orbit 102 may be carried out by any procedure. For example, the following satellite introduction steps may be used. .

Specifically, in this satellite introduction step, as an example, after launching the platform satellite P and the first mission satellite M1 by the same or different rockets in a state in which they are not coupled with each other, the platform satellite P and the It is coupled with the first mission satellite M1. Then, the platform satellite P coupled with the first mission satellite M1 is raised from the geostationary transfer orbit 102 to the geostationary orbit 101 .

Of the platform satellite P and the mission satellite M launched by the rocket, the platform satellite P is first separated from the rocket and put into the geostationary transfer orbit 102, and then the mission satellite M is separated from the rocket and put into the geostationary transfer orbit 102. may be

(Coupling of platform satellite P to mission satellite M)
First, the mission satellite M may be launched by a rocket and go around a predetermined orbit to perform a mission. After that, if the power supply system and/or the attitude orbit control system of the mission satellite M fails and a predetermined mission cannot be performed, the platform satellite P is launched by a rocket and the platform satellite P and the mission satellite M are coupled. good. (See Figure 8)

4 and 7, the first mission satellite M1 and/or the second mission satellite M2 are coupled to the platform satellite P orbiting the first orbit, but as shown in FIG. has a power supply system and/or an attitude orbit control system, and may be configured to be able to perform a mission independently without receiving power supply from the platform satellite P. At that time, the mission satellite M is configured to be detachably coupled to the platform satellite P, and if a failure occurs in the power supply system and/or the attitude start-up control system of the mission satellite M, coupling with the platform satellite P will occur. It may be configured to allow In this case, it can be said that the state in which the mission satellite M and the platform satellite P are combined corresponds to the state (1) in FIG. 4 or the first state in FIG. That is, the step of separating the first mission satellite M1 in (3) of FIG. 4 and FIG. 7 is performed after such a combining step. Alternatively, the mission satellite M and the platform satellite P may be discarded in a combined state. And, if the power supply system of the mission satellite M fails, power may be supplied from the connected platform satellite P. Alternatively, if the attitude orbit control system of the mission satellite M fails, the coupled platform satellite P may be configured to perform attitude orbit control.

By doing so, even if a mission satellite having a power supply system and/or an attitude orbit control system fails in orbit in either the power supply system or the attitude orbit control system and cannot perform a predetermined mission. Even so, the mission can continue utilizing the platform satellite's power system and/or attitude and orbital control system, and utilizing the mission capabilities that are still available. Therefore, the problem in the prior art of the high cost of remanufacturing a satellite, because the entire satellite is scrapped while the mission functions are still available, can be solved.

(Replacement of mission satellite M)
In the above embodiment, when the first mission satellite M1 has expired, the platform satellite P moves from the geostationary orbit 101 to the geostationary transfer orbit 102 to separate the first mission satellite M1. The first mission satellite M1 may be replaced by other conditions other than the expiration of the service life. For example, when the platform satellite P detects a failure of the first mission satellite M1 and receives a command signal to separate the first mission satellite M1 from the satellite management device 2, the platform satellite P separates the first mission satellite M1, It may be coupled with a second mission satellite M2 launched from the ground.

In the above embodiment, it was explained that the platform satellite P separates the first mission satellite M1, and then the second mission satellite M2 joins the platform satellite P. In addition to injecting the mission satellite M into another orbit such as the fourth orbit, the platform satellite P may move together with the mission satellite M to another orbit such as the fourth orbit. In other words, in one example of the satellite control method of the present invention, the platform satellite P has a mission satellite M (for example, a first mission satellite M1, a second mission satellite M2, or a third mission satellite different from the second mission satellite). ) are coupled, the platform satellite P may be moved to another orbit, such as the fourth orbit. It should be noted that the third mission satellite may be any mission satellite M that is coupled to the platform satellite P after the second mission satellite M2 has been separated from the platform satellite P, for example.

(Replacement of platform satellite P)
It is conceivable that the platform satellite P will fail (for example, equipment other than the communication device will fail) during operation of the artificial satellite 1 . In this case, the satellite management device 2 may control the satellites in the following manner. First, the satellite management device 2 selects, from among the plurality of platform satellites P orbiting the geostationary orbit 101, the second platform satellite P2 that can be coupled to the mission satellite M separated from the first platform satellite P1. A movement instruction command signal is transmitted to the 2-platform satellite P2 to move it to a predetermined position where it can be coupled to the mission satellite M. The satellite management device 2 transmits a separation instruction command signal for separating the mission satellite M to the failed first platform satellite P1.

The second platform satellite P2 receives the movement instruction command signal from the satellite management device 2 and moves toward the mission satellite M separated from the first platform satellite P1. Next, the first platform satellite P1 receives a separation instruction command signal from the satellite management device 2 and separates the mission satellite M. After that, the second platform satellite P2 is coupled to the mission satellite M so that the mission satellite M can continue to be used in the geostationary orbit 101 .

Although the present invention has been described above using the embodiments, the technical scope of the present invention is not limited to the scope described in the above embodiments, and various modifications and changes are possible within the scope of the gist thereof. be. For example, all or part of the device can be functionally or physically distributed and integrated in arbitrary units. In addition, new embodiments resulting from arbitrary combinations of multiple embodiments are also included in the embodiments of the present invention. The effect of the new embodiment caused by the combination has the effect of the original embodiment.

(Appendix)
The present application discloses the following inventions:
1. an orbital descent step of moving a platform satellite orbiting in a first orbit coupled with a first mission satellite to a second orbit closer to the earth than the first orbit; a separation step of separating the first mission satellite; a coupling step of coupling the second mission satellite inserted into the second orbit and the platform satellite; an orbit moving step of moving to one orbit or a third orbit different from the first orbit and the second orbit.

2. The separating step may include separating the first mission satellite from the platform satellite and injecting the first mission satellite into an orbit for entry into the atmosphere.

3. The above satellite control method further includes a time zone determination step of determining a time zone during which the platform satellite should reach the second orbit, wherein the time zone determination step includes determining a time zone during which the second mission satellite reaches the first orbit. determining a second time period for the platform satellite to reach the second orbit based on a first time period for the platform satellite to reach the second orbit; determining a third time period to initiate movement toward second orbit, wherein said orbital descent step causes said platform satellite to begin movement toward said second orbit during said third time period. may include steps.

4. The step of lowering the orbit may include moving the platform satellite to a predetermined position on the second orbit determined based on a position on the second orbit to be reached by the second mission satellite.

5. The first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit, and the orbit descending step initiates movement of the platform satellite to the geostationary transfer orbit, as transmitted by a satellite manager on the ground. The platform satellite may initiate movement from the geostationary orbit to the geostationary transfer orbit when the platform satellite receives a first command signal to.

6. The orbit moving step moves the platform satellite coupled with the second mission satellite to a predetermined position on the first orbit based on position information indicating the position where the second mission satellite should be positioned on the first orbit. A step of moving may be included.

7. The first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit, and the separating step includes a first mission satellite transmitted by a satellite management device on the ground for separating the first mission satellite from the platform satellite. The platform satellite may detach the first mission satellite based on two command signals.

8. The combining step comprises combining the platform satellite with the second mission satellite based on a third command signal transmitted by a satellite management device on the ground for combining the second mission satellite and the platform satellite. may contain.

9. The first orbit is a geostationary orbit, the second orbit is a geostationary transfer orbit, and the orbit movement step moves the platform satellite from the geostationary transfer orbit to the geostationary orbit transmitted by a satellite management device on the ground. moving said platform satellite to said geostationary orbit based on a fourth command signal to cause said platform satellite to move to said geostationary orbit;

10. In the above satellite control method, in a state where the platform satellite is coupled with the second mission satellite or a third mission satellite different from the second mission satellite, the platform satellite is put into an orbit for entering the atmosphere. It may further have a step of moving.

11. The platform satellite has a power generator, and the first mission satellite and the second mission satellite do not have a power generator, are detachably coupled to the platform satellite, and are powered by the platform satellite. may

12. The above satellite control method includes launching the platform satellite and the first mission satellite into the second orbit by the same or different rockets in a state in which they are not coupled with each other, and then launching the platform satellite and the first mission satellite into the second orbit. The method may further include a satellite introduction step of combining with one mission satellite and moving the platform satellite and the first mission satellite from the second orbit to the first orbit.

13. In the above satellite control method, prior to the orbit descent step, information indicating that the first mission satellite has failed, information indicating that the operation of the first mission satellite has ended, or A notification step may be further included in which the platform satellite or the first mission satellite transmits at least one of information indicating that an exchange is required to a satellite management device on the ground.

1 Artificial satellite 2 Satellite management device 10 Earth 21 Communication unit 22 Storage unit 23 Control unit 24 Data acquisition unit 25 Condition determination unit 26 Signal generation unit 27 Transmission unit 31 Solar paddle 32 Power supply unit 33 Coupling mechanism 34 Propulsion device 35 Attitude control device 36 communication device 37 control unit 41 coupling mechanism 42 mission device 43 power distribution device 44 communication device 45 control unit 101 geostationary orbit 102 geostationary transfer orbit M mission satellite M1 first mission satellite M2 second mission satellite P platform satellite P1 first platform satellite P2 2nd platform satellite S100 Satellite utilization system

Claims

from a platform satellite orbiting in conjunction with a first mission satellite in a first orbit and supplying power to said first mission satellite for said first mission satellite to perform a mission in said first orbit; a separation step separating the first mission satellite;
a coupling step of coupling the second mission satellite injected into the first orbit and the platform satellite;
a post-coupling step of causing said platform satellite coupled with said second mission satellite to orbit in said first orbit or move to another orbit different from said first orbit;
A satellite control method comprising:
The separating step comprises:
separating the first mission satellite from the platform satellite and injecting the first mission satellite into an orbit for entry into the atmosphere;
A satellite control method according to claim 1.
the separating step moves the platform satellite to another orbit different from the first orbit to separate the first mission satellite;
A satellite control method according to claim 1 or 2.
In a state where the platform satellite is coupled with the first mission satellite, the second mission satellite, or the third mission satellite different from the second mission satellite, the platform satellite is separated from the first orbit. further comprising moving to different trajectories;
A satellite control method according to claim 1 or 2.
the platform satellite has a power generator,
said first mission satellite and said second mission satellite having no power generator and being detachably coupled to said platform satellite and powered by said platform satellite;
A satellite control method according to claim 1 or 2.
The first mission satellite and/or the second mission satellite has a power supply system and/or an attitude orbit control system and is detachably coupled to the platform satellite, and the first mission satellite and/or the second mission satellite power is supplied from the platform satellite if there is a failure in the power system in the satellite;
The control method according to claim 1 or 2.
The first mission satellite and/or the second mission satellite has a power supply system and/or an attitude orbit control system,
Coupling the first mission satellite and/or the second mission satellite in which the power supply system and/or the attitude orbit control system has failed on the first orbit and the platform satellite;
A satellite control method according to claim 1 or 2.
discarding the platform satellite with the first mission satellite coupled to the platform satellite;
A satellite control method according to claim 1 or 2.
A platform satellite that orbits in a geostationary orbit that is a first orbit in conjunction with a first mission satellite, and that supplies power to the first mission satellite for the first mission satellite to perform a mission in the geostationary orbit. to a second orbit closer to the earth than the first orbit; and
separating the first mission satellite from the platform satellite in the second orbit;
a coupling step of coupling the second mission satellite inserted into the second orbit and the platform satellite;
an orbit movement step of moving the platform satellite coupled with the second mission satellite to the first orbit or a third orbit different from the first orbit and the second orbit;
A satellite control method comprising:
a platform satellite that orbits in conjunction with a first mission satellite in a first orbit and provides power to the first mission satellite for the first mission satellite to perform a mission in the first orbit; an orbital descent step for moving to a second orbit closer to the earth than the first orbit;
separating the first mission satellite from the platform satellite in the second orbit;
a coupling step of coupling the second mission satellite inserted into the second orbit and the platform satellite;
an orbit movement step of moving the platform satellite coupled with the second mission satellite to the first orbit or a third orbit different from the first orbit and the second orbit;
A satellite control method comprising: